Stator units



May 16, 1961 B. M. FIORI STATOR UNITS 2 Sheets-Sheet 1 Filed Aug. 22,1957 F IG I INVENTOF? BRUNO M F-"IOFU Evy/www ATTORNEY B. M. FIORISTATOR UNITS May 16, 1961 2 ,Sheets-Sheet 2 Filed Aug. 22, 1957 INVENTQRBRUNO M F-.QRI

United States PaferlfOf m M m m 2,984,454 m M e Y sTAToR i BrunoM,`Fiori, East Hartford,vConn., assignor to United .AircraftjCorporatiomEast Hartford, Conn., a corpora- 'ltpn of Delaware i Filed Aug. 22,1957, Ser. No. 679,623

f 1on1-rms. (Cl. 25a-77s) mit stator vane removal, once vthe `Powerplantrcombus# tion chambers have been removed, thru an access path axially"forward or upstream of the vanes as `taught in application Serial No.637,492, led January 31, 1957, now Patent No. 2,916,874, inthe name ofJohn Worobel. While this lis a definite improvement over thefabrications Which preceded it, it `was necessary touse a rig or fixtureto maintain all stator vanes in place while the damaged vane was removedand replaced.

It is an important object of this invention to teach a statorconstruction in which each vane is individually supported within thestator, independent of all other vanes.

It is afurther object of this invention to teach a stator constructionin which both the inner vane support and the outer vane support areone-piece units. i

It is still a further object of this invention to teachl a statorconstruction in which the individual 'vanes maybe locked in theirparticular position by a mechanism which, l if it' should break loose,would not enter the powerplant` gas Y:stream and further, in which thestatorjunit fabrication is such that .gas loading would tend to maintainthe component parts of the stator assembled, should the lock y mechanismdisengage.

It isstill a further object of this inventionto provide'ajstator unitwhich will permit release and removal of a' `particular stator vane thruan access path entirely on one side of the stator unit and preferably`upstream thereof,

without disturbing the other stator vanes.

It is aFfurther object of this invention toprovide Aa stator unit inwhich anti-erosion and thrust strips madef ofhard metals may `be'placedagainst the' downstream inner surface of the vane support where it 'willbe subjected to the vane thrust load and to the erosion effect oftheho't gases. Further, coolingair may be passed adjacent this thruststrip.

`It is still a further object of this invention to permit turbine rotorbladeinspectionr and removal by baring the rotor blades thru removal ofthe vanes ofthe adjacent stator unit. y

Other objects and advantages will be apparent from the followingspeciiication and the attached drawing in which:

Fig. 1 is a cross-sectional showing of my stator unit.

\Fi`g`.,2 is a viewtaken along line 2,-2 of Fig.` 1.

Figs. 3 and 4 show alternate connecting and locking means which maybeused to fasten the vane inner end tothe vane inner support.

Patented May 16, 196,1,

Patent No. 2,770,946, atmospheric air is introduced into` the compressorof a modern aircraft turbojet yengine and passed in compressed form intothe combustion chamber for heating. The heated and compressed air istheir` passed thru the turbine which performs a power extrae#1 tionfunction to drive the compressor and possibly a propeller, and afterpassing thru the turbine Vthe engine gases are discharged to atmospherethru an exhaust out;A4

let, thereby performing a propulsion function. j

Both the axial flow compressor and the axial ow tur? bine consistbasically Aof alternate rows of stationary vanes and moveable vanes,sometimes called blades. The stationary vanes are supported in positionas part of a` stator unit while the moveable blades rotate with a re-`volving disc. The stator unit andthe vanes thereon perform the functionof turning the Powerplant gas such that itis directed against therotating blades immediately .'downstream thereof at the proper angle.

Referring to Fig. 1, we see a partial showing of axial flow turbine 10having an axis or centerline `and rotor unit'12 which comprises aplurality of radially extendi ing blades 14 attached torand equallyspaced circumferentially about the periphery of disc 16 for rotation utherewith. Stator unit 18` comprises a plurality of stationary vanes 20which are `individually supported at their inner end by vane innersupport 22 and at their outer end by vane outer support 24. Vane outersupport 24 comprises axially directed ring l2.6 Iwhich forms acircleabout turbine and powerplant axis or centerline (not- A shown) and whichis supported by and may be integral Ring 26 carriesv with one-pieceouter turbine case l28. axially extending and radially spaced lips 30and32 at its forward end which form forwardly openingA lll-shapedchannelV 34. Ring 126 includes a` plurality ofradiallydirectedlholes 36lwhich are spaced' equally circumfer" entially' thereabout to receive,in positive fashionr'suclias" apnCh-t, or interlocking threads, radiallydirected outer vane support fpins or lugs 38. Ring26 `furthercomprises?v radiallydirected rflange 40 against which anti-erosionandfthrust strip 42 bears. Connecting means 44 attaches strip 42 to ring2'6 and may be in the form of a`rivet. "Coo1` ing air from passage 46 isdirected thru line 48 'and intot engine gas path 50 to perform thefunction of cooling@ stripi42. JThe" 'afterfor axially downstream end orsur-A` face 52 of vane platform `54 bears against strip 42andjtransmits: athrust load thereto, caused by the flowoff hot exhaust gasesacross vane 20. j

the axially downstream flange 64. Flange 62 has a plurality-.of axiallydirected apertures 7i) passingA therethruy'to receivein positivefashion, such as a pinch-t or interi locking thread, axially extendinginner vane support pin' or lug 72.

, A plurality lof stationaryvanes 20 areradiallydirectedl'f and equally,spaced `circumferentiallybet-Ween vane"V innerf support 22 and` vaneouter support 24 and each vanec20-` is positively positioned in statorunit 18, both` at -its inner,` end 74 and at its outer end 76,independently of all other; `vanes 20.`` lt will be noted that innerendr74. of vallei.`

stator unit illustratingl 3 2.0 .tamarins 'twg axially. flanges or lugs78 and 80 which are joined by member 82 and which are fabricated suchthat the inner surface 84 ofitheaxiallynforward flange `7 8, is ofgreater height and of'lesser radial ldistance from theiturbine axis thanis,-

inner. surface `86 csf-axially doWIlSiream llange 80. It will further benoted that surface 68 of support flange 64`eng`ages right angle` notch.88 of yflangel) in Suplportingfashion. r*In `assembled position, seeFig. 1, vane flange 78 is juxtapositioned to support flange 62, whilevaneY flange l80 is juxtapositioned to support flange l64 so'zthat thegas loading tends to seat vanes 20, Withvane 20 so positioned, inner pinor rivet 72, which is Vfirmly, lixed. `in axially forwardsupport vilange62 passes thru aperture 90 of vane flange 78 and extends axially forwardthereof and carries the necessary hole therethru to permit locking theparts in this position by the use of lock wire 92 such that the lockwire passes thru the two adjacent pins or rivets 72, as best shown inFig. 2.V

Figs. 3 and 4 show alternate vane inner end attaching and locking means.Fig. 3 shows bolt 94 passing thru vane flange 84 and support flange 62',into which it is lixedly threaded. Aperture 96 is provided to permitlocking bolt 94 in position by lock wire (not shown). Fig, 4 showsbolt.98 projecting thru vane flange 84" and support flange 6'2 andthreadedlyengaging insert 100 which is attached in any convenientfashion to support flange 62". Aperture 102 is provided to permit thelocking of bolt 98 in position by means ofV lock wirer (not shown).y A

By referring to Fig. l, it will be noted that vane inner. end 74 isaxially positioned by support flanges 62 and 64 and is crcumferentiallyand radially fixed by rivet, lug or pin 72. vAt the outer end 76 of vane20, axially extending platform 54 is received loosely by pin or lug 38to axially Aand circumferentially position outer end 76 of vane 20 and asubstantial radial distance exists .between vane platform 54 and ring 26of vane outer support 24, thereby permitting relative radial movementtherebetween. Lug 38 preferably passes thru platform 54 in a location tobe substantially equidistant between the side walls of vane L20.

As shown in Fig. 1, transition duct 104 is located immediately upstreamor axially forward of stator unit 18 and engages outer vane support 24in sealing relation by seal 106 and engages inner vane flange 78 insealing relation by seal'i108. Surface 109 of seal 108 is positioned toprovide axial support to the vane inner end thru flange 78 in case ofback pressure or backfire. Reverse axial loading goes from ange 78 toseal 108, to transition duct i104 and to support member 126. Transitionduct 104 and combustion chamber support 110 may be removed bydisengaging connecting means 112 and 114 after the combustion chamber(not shown) has been removed. This bares lock wire 92 for removal, whichwill permit the removal of bolts 94 and 98 in Figs. 3 and 4,respectively, to free the inner ends 74 of vane 20 in the conligurationsshown in Figs. 1, 3 and 4, thereby permitting same to be moved radiallyinward, if desired, and then pivoted axially forward about pin 38 ormerely pivoted axially forward about pin 38 due to the loose litexisting between 'pin 38 and platform 54, thereby releasing the outerend 76 of vane 20 to free the vane for removal from stator unit 18.

'It will be noted that a single vane 20 may be released, removed andreplaced thru access from the upstream or axially forward side of statorunit 18 only, without disturbingthe .other vanes in any way.

As best shown in Fig. 5, it is possible to assemble and disassemble anynumber of vanes '20 or an individual vane 20 without disturbing any ofthe remaining vanes. In assembling the entire unit, rotor 16, outer case28 and inner case 60 are fastened inV position. Each vane will beassembled in'turn' by utilizing the access hole'defined between cases 28and 60 on the forwardfside of Spaedand radially directed rotor 1 6 byintroducing the vane toouteryane support 24 with the vane inner end 74axially forward of the vane outer end 76, in tilted fashion, such that apreliminary connection may be made between lug 38 and platform 54,whereupon vane 20 will be pivoted clockwise about pin 38 into theposition shown in Fig. l in which vane flange 78 engages lugY 72. Thisassembly is possible since pin 72 is heldin position by a tight it inllange 62 and extends loosely through aperture 90 in ange 94 whileinlike manner pin 83 passesrloosely through the aperture in vane platforml54. l Lock Wire 92 will then be fastened in position as shown in Fig. 2and the transition duct 104, the burner after support and the combustionchambers will be assembled. It will be noted that lock wire 92 isconfined within chamber 116 such that if a rupture should occur thereinand a piece break loose therefrom during operation, the piece would notfall into .gas passage 50. ASeal `118 is carried by cylindrical support120 and performs the function ofpreventing air flow between gas passage50 and chamber 1,22. Support 120 is fastened to vane inner support `22by any convenient means such as welding or brazing, and.

vane inner support 22 isy attached to structural members 126 of turbine10 byconnecting means 124. In known fashion, the engine case orcombustion chamber case, may then be placed in position to envelop theseries of,

combustion chambers.

To replace a singlevane 20, it is merely necessary to remove thecombustion chamber case (not shown), to. remove the combustion chamberand transition duct,104 and thereby gain access to vanes'20 from theaxially forward side thereof. Lockwire 94 is then removed, whereuponvane 20 may be tilted forwardly in itsinner end to pivot slightly aboutpin 38. This pivot action frees the inner end of thevane from ange 64,whereupon the vane may bey moved radially inwardly to clearpin 38 andthen moved axially forwardly in complete freedom.

.Although the preferred embodiments have been shown and described, itwill be apparent that various changes and modifications may be made inthe construction and arrangement of the various parts without departingfrom the scope of this novel concept.

I claim:

1. A stator unit of circular cross-section for use in a powerplanthaving an axis comprising a plurality of vanes, each having a hole inone end thereof, means for supporting each of said vanes in itsoperative position to be substantially radially extending andsubstantially van equal radial distance from and equally spaced in acircle.l about said axis, means providing access to one side of.'

said vanes and support means, and said support means including aAplurality of substantially radially extending pins each receivedloosely in one of said holes in said vanes and a plurality of readilyreleasable means each accessible from .said one side and each fullysupporting the other end of one of said vanes thereby permitting theremoval and replacement of any vane in said plurality from said onesidewhile maintaining all other vanes in Y operative position.

2. A .stator unit of circular cross-section for use in a powerplanthaving an axis comprising a plurality of vanes, each having a hole inthe outer end thereof, means to4 support said vanes to be substantiallyradially extending and substantially an equal radial distance from andequally spaced in a circle aboutY said axis including first meanssupporting the outer end of each of said .vanes individually andindependently of all other vanes and second means independent of saidfirst means supporting the inner end of each of said vanes individuallyand inden pendently of all other vanes Vsaid rst means including a ringenveloping said vanes and having a plurality of substantially radiallyinwardly directed pins each received loosely in one of said holes insaid vanesV and said second,

means including a plurality of readily releasable means porting each ofsaid vanes in its operative position to be substantially radiallyextending and substantially an equal radial distance from and equallyspaced in a circle about said axis, and means providing access to saidside of said vanes and support means.

4. A stator unit comprising a vane outer support cornprising a ring, avane inner support comprising at least one radially extending circularflange, a plurality of vanes each having an axially extending platformat its outer end and at least one radially extending ilange at its innerend and with said vanes extending radially between and spacedcircumferentially about said vane supports and each located with respectthereto such that said radially extending flanges are juxtapositionedand further such that said vane outer support ring and each of said vaneplatforms is spaced a preselected distance apart radially, a pluralityof radially directed lugs each connected to said vane outer support ringand projecting loosely thru one of said vane platforms to position thevane outer end, a plurality of axially directed lugs each connected tosaid vane inner support flange and projecting thru the inner end flangeof one of said vanes and projecting therebeyond to position said vaneinner end, and means removable from one side of said stator unit lockingeach of said vane anges in position individually against said supportflange and on one of said axial lugs thereby permitting one of saidvanes to be released, removed and replaced thru access from one Side ofsaid stator unit only while all other vanes are maintained in position.

5. A stator unit having an axis and comprising a vane outer supportcomprising a ring, a vane inner support comprising two axially spacedrings forming radially extending circular ilanges of different innerdiameters such that the axially forward flange is of lesser diameter, aplurality of vanes each having an axially extending platform at itsouter end and two axially spaced radially extending flanges at its innerend and with the axially forward vane flange of greater height and withsaid vanes extending radially between and spaced circumferentially aboutsaid vane supports and each located with respect thereto such that saidradially extending flanges are juxtapositioned with said axially forwardvane iange engaging the axially forward support flange on the axiallyforward side thereof and with the other flanges engaging in the samerelative axial positions and further such that said vane outer supportring and each of said vane platforms is spaced a preselected distanceapart radially, a plurality of radially directed lugs each connected tosaid vane outer support ring and projecting loosely thru one of saidvane platforms to position the vane outer end, a plurality of axiallydirected lugs each connected to said axially forward inner supportflange and projecting thru the axially forward inner end flange of oneof said vanes and projecting therebeyond to position said vane innerend, and means removable from one side of said stator unit locking eachof said vane flanges in position individually against said supportflange and on one of said axial lugs thereby permitting one of saidvanes to be released, removed and replaced thru access from one side ofsaid stator unit only while all other vanes are maintained in position.

6. A stator unit having an axis and comprising a vane outer supportcomprising an axially extending ring forming a circle about said axis,an anti-erosion and thrust ring attached to said vane outer supportring, cooling gas passages in said outer support ring positioned todirect Cooling sas carer Said-,antil-emsionand thrustting, axane innersupport olprisins .two axially spaced. Lfilles; termf ing radiallyextending circular `flanges of different imeljdiamcters such that theaxially forward flange is of lesser diameter; ai pluralityaof` vaneseach ,havinganfaxially extending platformat itsouter endand-twoaxiallyspaced radially extendirig"tlaiiges at its inne' end uand with theaxia11yrorwgd vane-aange- Vof greater' height and with said vanesextending radially Vbetween and spaced circumferentially about said vanesupports and each located with respect thereto such that said radiallyextending anges are juxtapositioned with said axially forward vaneflange engaging the axially forward support flange on the axiallyforward side thereof yand with the other flanges engaging in the samerelative axial positions and further such that said vane outer supportring and each of said vane platforms is spaced a preselected distanceapart radially, and further such that the after end of said platformbears against said anti-erosion and thrust ring, a plurality of-radially directed lugs each connected to said vane outer support ringand projecting loosely thru one of said vane platforms to position thevane outer end, a plurality of axially `directed -lugs each connected tosaid axially -forward vane inner support flange and projecting thru theaxially forward inner end flange of one of said vanes and projectingtherebeyond to position said vane inner end, and means removable fromone side of said stator unit locking each of said vane flanges inposition individually against said support flange and on one of saidaxial lugs thereby permitting one of said vanes to be released, removedand replaced thru access from one side of said stator unit only whileall other vanes are maintained in position.

7. A turbine or compressor unit having an axis and comprising a rotorunit and a stator unit coaxial therewith and positioned axially forwardthereof,l said rotor unit comprising a plurality of removable radiallyextending blades attached to the periphery of a rotatable disc andequally spaced thereabout, said stator runit. comprising a vane outersupport comprising an axially extending ring forming a circle about saidaxis, an anti-erosion and thrust ring attached to said vane outersupport ring, cooling gas passages in said outer support ring positionedto direct cooling gas over said anti-erosion and thrust ring, a vaneinner support comprising two axially spaced rings forming radiallyextending circular flanges of different inner diameters such that theaxially forward flange is of lesser diameter, a plurality of vanes`aligned with said blades each having an axially extending platform atits outer end and two axially spaced radially extending flanges at itsinner end and with the axially forward vane flange of greater height andwith said vanes extending radially between and spaced circumferentiallyabout said vane supports and each located with respect thereto such thatsaid radially extending flanges are juxtapositioned with said axiallyforward vane flange engaging the axially yforward support flange on theaxially forward side thereof and with the other flanges engaging in thesame relative axial positions and further such that said vane outersupport ring and each of said vane platforms is spaced a preselecteddistance apart radially and further such that the v after end of saidplatform bears against said :anti-erosion and thrust ring, a pluralityof radially directed lugs each connected to said vane outer support ringand projecting loosely thru one of said vane platforms to position thevane outer end, a plurality of axially directed lugs each connected tosaid axially forward vane inner support flange and projecting thru theaxially forward inner end flange of one of said vanes and projectingtherebeyond to position said vane inner end, and means removable fromone side of said stator unit locking each of said vane flanges inposition individual-ly against said support flange and on one of saidaxial lugs thereby permitting one of said vanes to be released andremoved individually and independently of Vall other vanes thru accessfrom one side

